Aero-engine lubricating system
By designing an automatic adjustment lubrication system in an aircraft engine and controlling the oil circulation mode with bypass valves and oil radiators, the problem of poor lubrication effect caused by fluctuations in the engine oil temperature is solved, and the reliability of engine lubrication and lightweight parts are achieved. .
Patent Information
- Application Number
- CN202421313652.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-11
- Publication Date
- 2025-01-17
- Estimated Expiration
- 2034-06-11
AI Technical Summary
The oil temperature fluctuates greatly in high cold, high heat and high altitude environments, resulting in poor lubrication effect, affecting service life, and high lightweight requirements. It is necessary to design a lubrication system with a simple and light structure to adapt to temperature changes.
An aircraft engine lubrication system is designed, including a thermostat seat, bypass valve, oil pump, oil filter element and oil radiator. The oil circulation mode is automatically controlled through the bypass valve, and the lubricating part is directly supplied at low temperatures, and heat dissipation is carried out at high temperatures. The unit cools down and switches the small cycle mode when necessary to maintain a reasonable temperature.
It realizes automatic adjustment of engine oil under different temperature environments, ensuring engine lubrication reliability and lightweight parts, and is suitable for use in the aviation field.
Smart Images
Figure CN222363035U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of aviation engines, in particular to an aviation engine lubrication system. Background Art
[0002] The four-stroke aviation piston exhaust gas turbocharger engine is a product that is adapted to the high-cold, high-heat and high-altitude use environment. The use environment temperature varies greatly (between -40℃ and +80℃), and there are rapid changes in the ambient temperature caused by the need for rapid warm-up and rapid take-off. At the same time, the high-altitude cruising environment temperature is low and there is a risk of overcooling the engine oil by the ram air oil radiator. Therefore, when the aircraft engine is working during a flight, there is a situation where the lubricating oil temperature fluctuates greatly.
[0003] As we all know, in the engine warm-up stage under low temperature environment, the oil temperature is low and the viscosity is too large, so the resistance brought by lubrication is large. In high temperature and high load environment, the oil temperature is too high, resulting in poor lubrication effect, accelerated oil aging and deterioration, and affecting the service life of the oil. Furthermore, in order to ensure the lubrication of the supercharger bearing, the aircraft engine needs to provide a separate oil circuit, and to ensure sufficient heat dissipation in high temperature environment, a ram air cooling oil radiator is set. On the other hand, the requirements for lightweight aircraft engine parts are high. Therefore, it is necessary to design a lubrication system with a simple and lightweight structure and the ability to implement different supply lines according to the temperature of the oil. Utility Model Content
[0004] Therefore, in order to solve the above problems, the utility model provides an aircraft engine lubrication system, which can implement different supply lines according to the temperature of the engine oil to ensure reliable lubrication of the engine while achieving a light structure.
[0005] To achieve the above purpose, the technical solution provided by the utility model is as follows:
[0006] An aircraft engine lubrication system comprises: a thermostat seat, a bypass valve equipped with a thermostat, a thermostat seat fixing bolt, an oil pump, an oil filter element and an oil radiator; the thermostat seat is fixed to the engine by the thermostat seat fixing bolt, the oil filter element is fixed to the thermostat seat, and the thermostat seat fixing bolt has a hollow channel;
[0007] The thermostat seat is provided with a first cavity, a second cavity, a first oil port connected to the first cavity, and a second oil port connected to the second cavity; the bypass valve is connected to the first cavity and the second cavity; the thermostat controls the on-off of the bypass valve; the first oil port is connected to the inlet of the oil radiator, and the outlet of the oil radiator, the second oil port and the oil inlet of the supercharger are connected;
[0008] The inlet of the oil filter is connected to the second cavity of the thermostat seat, the outlet of the oil filter is connected to the main oil channel of the engine through the hollow channel of the thermostat seat fixing bolt, the inlet of the oil pump is connected to the engine oil pan, and the outlet of the oil pump is connected to the first cavity of the thermostat seat.
[0009] Furthermore, the first cavity of the thermostat seat has a first opening, the second cavity has a second opening, and the first opening and the second opening are arranged opposite to each other, the first opening of the thermostat seat is arranged toward the engine and is sealed and assembled on the engine housing; the oil filter element is sealed and assembled on the second opening of the thermostat seat; the thermostat seat fixing bolt passes through the oil filter element, the second cavity, the first cavity to the main oil channel of the engine.
[0010] Furthermore, a return spring is installed in the bypass valve, and the return spring is compressed when the thermostat is heated and stretched to block the bypass valve.
[0011] Furthermore, the valve housing of the bypass valve is integrally formed with the thermostat seat.
[0012] Furthermore, the oil outlet of the supercharger is connected to the engine oil pan.
[0013] An operating method of the aircraft engine lubrication system as described above, when the oil is below the set temperature, the bypass valve is in an open state, the oil pump draws oil from the engine oil pan and sends it to the first cavity of the thermostat seat, the oil then enters the second cavity through the bypass valve, and then the oil is divided into two paths, one path of oil is filtered through the oil filter element, and flows to the main oil channel of the engine through the hollow channel of the thermostat seat fixing bolt to lubricate the engine's various moving friction pairs; the other path enters the supercharger through the second oil port to lubricate the supercharger; when the engine oil temperature rises, the thermostat The thermostat starts to work. When the temperature is greater than the set temperature, the bypass valve is completely closed by the thermostat. The oil pump draws oil from the engine oil pan and sends it to the first cavity of the thermostat seat. After that, the oil enters the oil radiator from the first oil port to achieve cooling. The cooled oil flows out from the outlet of the oil radiator and is divided into two paths. One path flows to the supercharger to lubricate the supercharger; the other path flows to the second cavity through the second oil port, and then flows into the oil filter element for filtration. The filtered oil flows to the main oil channel of the engine through the hollow channel of the thermostat seat fixing bolt to lubricate the engine's various moving friction pairs.
[0014] The technical solution provided by the utility model has the following beneficial effects:
[0015] 1. With the lubrication system of this solution, when the oil temperature is low (i.e., lower than the set temperature), the oil is directly circulated and supplied through the bypass valve without passing through the oil radiator. The oil runs in a small circulation mode, and the oil output by the oil pump directly lubricates the engine and supercharger, ensuring that the oil quickly reaches the lubrication parts while also accelerating the warm-up of the engine. When the oil temperature is high (i.e., higher than the set temperature), the oil runs in a large circulation mode, and the oil is cooled through the oil radiator. Once excessive oil cooling occurs during high-altitude cruising, the oil temperature can be switched back to a small circulation to ensure a suitable oil temperature when it drops. The large and small circulation modes of the oil are automatically controlled by the set oil temperature. With such a system, the engine oil can be kept within a certain reasonable temperature range.
[0016] 2. The thermostat seat is fixed to the engine by the thermostat seat fixing bolts, the oil filter element is fixed to the thermostat seat, and the outlet of the oil filter element is connected to the main oil channel of the engine through the hollow channel of the thermostat seat fixing bolts. The structure is compact and simple, which can well realize the lightweight of parts and components, and is more suitable for use in the aviation field. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 The figure shows a schematic diagram of the structure of the aircraft engine lubrication system in the embodiment, in which the system is in a small cycle operation state;
[0018] Figure 2 The diagram shows the structure of the aircraft engine lubrication system in the embodiment, which is in a large-circulation operation state. DETAILED DESCRIPTION
[0019] To further illustrate the various embodiments, the present invention provides drawings. These drawings are part of the disclosure of the present invention, which are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, a person of ordinary skill in the art should be able to understand other possible implementations and advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are generally used to represent similar components.
[0020] In the description of the present invention, terms such as "upper", "lower", "left", "right", "front", "backward", etc., and the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.
[0021] The utility model is now further described in conjunction with the accompanying drawings and specific implementation methods.
[0022] Reference Figure 1 and Figure 2As shown, the present embodiment provides an aircraft engine lubrication system, comprising: a thermostat seat 10, a bypass valve 30 equipped with a thermostat 31, a thermostat seat fixing bolt 40, an oil pump 50, an oil filter element 20 and an oil radiator 60; the thermostat seat 10 is fixed to the engine 1 by the thermostat seat fixing bolt 40, the oil filter element 20 is fixed to the thermostat seat 10, and the thermostat seat fixing bolt 40 has a hollow channel 41.
[0023] The thermostat seat 10 is provided with a first cavity 101, a second cavity 102, a first oil port 11 connected to the first cavity 101, and a second oil port 12 connected to the second cavity 102. The bypass valve 30 connects the first cavity 101 and the second cavity 102; the thermostat 31 controls the on-off of the bypass valve 30; specifically, when the oil temperature is lower than the set temperature (such as the set temperature is 85°C in this embodiment), the bypass valve 30 is in an open state; when the oil temperature is higher than the set temperature, the thermostat 31 extends and closes the bypass valve 30, even if the bypass valve 30 is disconnected (i.e. closed). The first oil port 11 is connected to the inlet of the oil radiator 60, and the outlet of the oil radiator 60, the second oil port 12 and the oil inlet of the supercharger 70 are connected. Specifically, the outlet of the oil radiator 60, the second oil port 12 and the oil inlet of the supercharger 70 can be connected through a three-way pipe.
[0024] The inlet of the oil filter 20 is connected to the second cavity 102 of the thermostat seat 10, and the outlet of the oil filter 20 is connected to the main oil channel of the engine 1 through the hollow channel 41 of the thermostat seat fixing bolt 40. The inlet of the oil pump 50 is connected to the engine oil pan, and the outlet of the oil pump 50 is connected to the first cavity 101 of the thermostat seat 10.
[0025] Thus, there are two paths from the first cavity 101 to the second cavity 102 , one directly passing through the bypass valve 30 , and the other passing through the oil radiator 60 .
[0026] This embodiment also provides an operation method based on the above-mentioned aircraft engine lubrication system, when the engine oil is below a set temperature (such as when starting a cold engine), Figure 1 As shown, the bypass valve 30 is in an open state, the oil pump 50 extracts oil from the engine oil pan and sends it to the first cavity 101 of the thermostat seat 10, and the oil enters the second cavity 102 through the bypass valve 30, and then the oil is divided into two paths, one path of the oil is filtered through the oil filter element 20, and flows to the main oil channel of the engine 1 through the hollow channel 41 of the thermostat seat fixing bolt 40 to lubricate the various moving friction pairs of the engine 1. After lubrication, the oil in the engine 1 will flow back to the engine oil pan to achieve circulation; the other path enters the supercharger 70 through the second oil port 12 to lubricate the supercharger 70. Specifically, the oil supply cycle through the bypass valve 30 is defined as a small cycle.
[0027] When the engine oil temperature rises, the thermostat 31 starts to work. When the temperature is greater than the set temperature, the bypass valve 30 is completely closed by the thermostat 31. Figure 2 As shown, the oil pump 50 extracts the oil from the engine oil pan and sends it to the first cavity 101 of the thermostat seat 10, and then enters the oil radiator 60 from the first oil port 11 to achieve cooling. The cooled oil flows out from the outlet of the oil radiator 60 and is divided into two paths, one of which flows to the supercharger 70 to lubricate the supercharger 70; the other flows to the second cavity 102 through the second oil port 12, and then flows into the oil filter 20 through the second cavity 102 for filtration. The filtered oil flows to the main oil channel of the engine 1 through the hollow channel 41 of the thermostat seat fixing bolt 40 to lubricate the various moving friction pairs of the engine 1. Specifically, the oil supply cycle through the oil radiator 60 is defined as the large cycle.
[0028] With the lubrication system of this solution, when the oil temperature is low (i.e., lower than the set temperature), the oil is directly circulated and supplied through the bypass valve 30 without passing through the oil radiator 60. The oil runs in a small circulation mode, and the oil output by the oil pump 50 directly lubricates the engine 1 and the supercharger 70, which ensures that the oil quickly reaches the lubrication parts while also accelerating the warm-up of the engine. When the oil temperature is high (i.e., higher than the set temperature), the oil runs in a large circulation mode, and the oil is cooled through the oil radiator 60. Once excessive heat dissipation of the oil occurs during high-altitude cruising, the oil temperature can be switched back to a small circulation to ensure a suitable oil temperature when it drops. The large and small circulation modes of the oil are automatically controlled by the set oil temperature. With such a system, the oil of the engine 1 can be kept within a certain reasonable temperature range.
[0029] The thermostat seat 10 is fixed to the engine 1 by the thermostat seat fixing bolts 40, and the oil filter element 20 is fixed to the thermostat seat 10. The outlet of the oil filter element 20 is connected to the main oil channel of the engine 1 through the hollow channel 41 of the thermostat seat fixing bolts 40. The structure is compact and simple, and can well achieve lightweight components, and is more suitable for use in the aviation field.
[0030] Specifically, in this embodiment, the oil outlet of the supercharger 70 is connected to the engine oil pan, and the oil input to the supercharger 70 flows back to the engine oil pan after lubrication to achieve recycling.
[0031] The first cavity 101 of the thermostat seat 10 has a first opening, the second cavity 102 has a second opening, and the first opening and the second opening are arranged opposite to each other, which is convenient for processing and can better reduce the weight of the thermostat seat 10. The first opening of the thermostat seat 10 is arranged toward the engine 1 and is sealed and assembled on the housing of the engine 1; the oil filter 20 is sealed and assembled on the second opening of the thermostat seat 10; the thermostat seat fixing bolt 40 passes through the oil filter 20, the second cavity 102, the first cavity to the main oil passage of the engine 1. Specifically, the sealing cooperation between the thermostat seat 10 and the engine 1 and the sealing cooperation between the oil filter 20 and the thermostat seat 10 are both achieved by the sealing abutment of the sealing ring, which has a simple structure and good sealing effect.
[0032] Further preferably, a return spring 32 is installed in the bypass valve 30, and when the thermostat 31 is heated and stretched to block the bypass valve 30, the return spring 32 is compressed to store energy, and when the standby oil temperature drops below the set temperature, the thermostat 31 retracts, and the return spring 32 is reset and applies elastic force to the thermostat 31, so that the thermostat 31 can retract relatively quickly, thereby opening the bypass valve 30. Of course, in other embodiments, the structure of the return spring 32 may not be adopted.
[0033] The valve housing of the bypass valve 30 is integrally formed with the thermostat seat 10 , eliminating the need to assemble the bypass valve 30 and the thermostat seat 10 , saving assembly operations and avoiding the problem of oil leakage caused by improper assembly.
[0034] Although the present invention has been specifically demonstrated and described in conjunction with the preferred embodiments, those skilled in the art should understand that various changes may be made to the present invention in form and detail without departing from the spirit and scope of the present invention as defined in the appended claims, all of which are within the scope of protection of the present invention.
Claims
1. An aircraft engine lubrication system, characterized in that: include: A thermostat seat, a bypass valve equipped with a thermostat, a thermostat seat fixing bolt, an oil pump, an oil filter element and an oil radiator; the thermostat seat is fixed to the engine by the thermostat seat fixing bolt, the oil filter element is fixed to the thermostat seat, and the thermostat seat fixing bolt has a hollow channel; The thermostat seat is provided with a first cavity, a second cavity, a first oil port connected to the first cavity, and a second oil port connected to the second cavity; the bypass valve is connected to the first cavity and the second cavity; the thermostat controls the on-off of the bypass valve; the first oil port is connected to the inlet of the oil radiator, and the outlet of the oil radiator, the second oil port and the oil inlet of the supercharger are connected; The inlet of the oil filter is connected to the second cavity of the thermostat seat, the outlet of the oil filter is connected to the main oil channel of the engine through the hollow channel of the thermostat seat fixing bolt, the inlet of the oil pump is connected to the engine oil pan, and the outlet of the oil pump is connected to the first cavity of the thermostat seat.
2. The aircraft engine lubrication system according to claim 1, characterized in that: The first cavity of the thermostat seat has a first opening, the second cavity has a second opening, and the first opening and the second opening are arranged opposite to each other. The first opening of the thermostat seat is arranged toward the engine and is sealed and assembled on the engine housing; the oil filter element is sealed and assembled on the second opening of the thermostat seat; the thermostat seat fixing bolt passes through the oil filter element, the second cavity, the first cavity to the main oil channel of the engine.
3. The aircraft engine lubrication system according to claim 1, characterized in that: A return spring is installed in the bypass valve, and the return spring is compressed when the thermostat is heated and stretched to block the bypass valve.
4. The aircraft engine lubrication system according to claim 1 or 3, characterized in that: The valve housing of the bypass valve is integrally formed with the thermostat seat.
5. The aircraft engine lubrication system according to claim 1, characterized in that: The oil outlet of the supercharger is connected to the engine oil sump.